Abstract
The sensibility analysis of the factors to crack growth life has been done. The results show that the input parameters have the following precedence ordering: fatigue crack growth threshold, fracture spectrum, initial crack, fracture toughness, the sensibility values are 11.25, 8.5417, 0.8333, 0.1125, respectively. The model parameters have the following precedence ordering: n, p, C, q. the sensibility values are 6.0417, -3.9583, 1.25, 0.1812, respectively. The reliability analysis was conducted by Monte-Carlo method, the results show that the crack growth life accord with lognormal distribution. The lives with different reliability were obtained. The reliability analysis results of the crack growth life has provided the data for a hybrid approach based on a mixture of the traditional safe-life and damage tolerance techniques which were used as an optimal strategy for ensuring the helicopter structural integrity.
Sign-in/Register to access full text options 
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a callDisclaimer: All third-party content on this website/platform is and will remain the property of their respective owners and is provided on "as is" basis without any warranties, express or implied. Use of third-party content does not indicate any affiliation, sponsorship with or endorsement by them. Any references to third-party content is to identify the corresponding services and shall be considered fair use under The CopyrightLaw.
